Patents by Inventor Marco Link
Marco Link has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
-
Publication number: 20230144467Abstract: A gas burner comprises an automatic firing unit for regulating or controlling an amount of gas supplied to the gas burner via a gas control valve and a lambda probe (1) arranged in the exhaust gas flow for measuring a residual oxygen content in the exhaust gas. A method for operating the gas burner comprises a first operating state in which the gas burner is operated in standard mode, wherein the residual oxygen content in the exhaust gas is regulated via the measured value of the lambda probe (1).Type: ApplicationFiled: March 22, 2021Publication date: May 11, 2023Inventors: Eugen GLEIM, Marco LINK
-
Patent number: 10408135Abstract: A method for operating a gas turbine below the nominal power includes: determining a lower power threshold value of the gas turbine which causes the gas turbine to leave a CO-emission-compliant partial load range of the gas turbine; providing a specified threshold value for output gas turbine power, wherein the specified threshold value is less than the nominal power of the gas turbine; and operating the gas turbine at an output gas turbine power above the specified threshold value at a constant exhaust gas temperature, wherein the inlet guide blades of a compressor of the gas turbine are closed further in order to reduce the output gas turbine power. A sufficiently large valve is selected for the specified threshold value so that increases of the primary zone temperature, combustion temperature, and exhaust temperature extend over a CO-emission-compliant partial load range of the gas turbine that is as large as possible.Type: GrantFiled: February 12, 2014Date of Patent: September 10, 2019Assignee: Siemens AktiengesellschaftInventors: Thorsten Engler, Markus Gorynski, Manuel Gutermuth, Philipp Kreutzer, Marco Link, Nicolas Savilius, Kai Suselbeck, Marc Tertilt
-
Patent number: 9915166Abstract: A gas turbine includes an intake tract and a compressor having a compressor flow channel. The compressor further includes an inlet guide vane row positioned in the compressor flow channel having inlet guide vanes that can be adjusted. The gas turbine has an icing sensor unit having at least one sensor arranged between a first compressor blade row and a first compressor guide vane row. The first compressor blade row is thereby arranged in the compressor flow channel directly downstream of the inlet guide vane row, and the first compressor guide vane row is arranged directly downstream of the first compressor blade row. A method detects an imminent icing of the compressor, and the compressor is safeguarded therefrom such that at least inlet guide vanes of the inlet guide vane row are adjusted such that the acceleration of an intake air mass flow is reduced.Type: GrantFiled: February 20, 2014Date of Patent: March 13, 2018Assignee: Siemens AktiengesellschaftInventors: Thorsten Engler, Markus Gorynski, Manuel Gutermuth, Philipp Kreutzer, Marco Link, Nicolas Savilius, Kai Suselbeck, Marc Tertilt
-
Patent number: 9574449Abstract: An internally coolable component for a gas turbine with at least one cooling duct, on the inner surface of which swirl elements are arranged in the form of turbulators which extend transversely with respect to the main flow direction of a coolant is provided. In order to reduce pressure losses for the coolant in the cooling duct, pins with different heights are set up between the turbulators.Type: GrantFiled: August 2, 2012Date of Patent: February 21, 2017Assignee: SIEMENS AKTIENGESELLSCHAFTInventors: Marcel Eifel, Daniel Gloss, Andreas Heselhaus, Stephan Klumpp, Marco Link, Uwe Sieber, Stefan Volker, Michael Wagner
-
Publication number: 20160024960Abstract: A gas turbine includes an intake tract and a compressor having a compressor flow channel. The compressor further includes an inlet guide vane row positioned in the compressor flow channel having inlet guide vanes that can be adjusted. The gas turbine has an icing sensor unit having at least one sensor arranged between a first compressor blade row and a first compressor guide vane row. The first compressor blade row is thereby arranged in the compressor flow channel directly downstream of the inlet guide vane row, and the first compressor guide vane row is arranged directly downstream of the first compressor blade row. A method detects an imminent icing of the compressor, and the compressor is safeguarded therefrom such that at least inlet guide vanes of the inlet guide vane row are adjusted such that the acceleration of an intake air mass flow is reduced.Type: ApplicationFiled: February 20, 2014Publication date: January 28, 2016Applicant: Siemens AktiengesellschaftInventors: Thorsten Engler, Markus Gorynski, Manuel Gutermuth, Philipp Kreutzer, Marco Link, Nicolas Savilius, Kai Suselbeck, Marc Tertilt
-
Publication number: 20160010566Abstract: A method for operating a gas turbine below its rated power, in which CO emissions in the exhaust gas of the gas turbine increase with a reduction of the output gas turbine power, wherein, if a predefined threshold value, which can be selected as desired, for the CO emissions is reached or if a predefined threshold value, specified in relative or absolute terms, for the output gas turbine power is undershot, the combustion temperature in the combustion chamber of the gas turbine is increased. To operate the gas turbine with low emissions, for a constant power output, the exhaust-gas temperature increase generated at the outlet of the gas turbine as a result of the combustion temperature increase is at least partially compensated through the addition of a liquid or vaporous medium.Type: ApplicationFiled: February 6, 2014Publication date: January 14, 2016Applicant: Siemens AktiengesellschaftInventors: Andreas Bottcher, Eberhard Deuker, Andre Kluge, Philipp Kreutzer, Marco Link, Ansgar Sternemann, Marc Tertilt, Martin Wilke
-
Publication number: 20150369137Abstract: A method for operating a gas turbine below the nominal power includes: determining a lower power threshold value of the gas turbine which causes the gas turbine to leave a CO-emission-compliant partial load range of the gas turbine; providing a specified threshold value for output gas turbine power, wherein the specified threshold value is less than the nominal power of the gas turbine; and operating the gas turbine at an output gas turbine power above the specified threshold value at a constant exhaust gas temperature, wherein the inlet guide blades of a compressor of the gas turbine are closed further in order to reduce the output gas turbine power. A sufficiently large valve is selected for the specified threshold value so that increases of the primary zone temperature, combustion temperature, and exhaust temperature extend over a CO-emission-compliant partial load range of the gas turbine that is as large as possible.Type: ApplicationFiled: February 12, 2014Publication date: December 24, 2015Applicant: Siemens AktiengesellschaftInventors: Thorsten Engler, Markus Gorynski, Manuel Gutermuth, Philipp Kreutzer, Marco Link, Nicolas Savilius, Kai Suselbeck, Marc Tertilt
-
Publication number: 20150027128Abstract: A heat-shield element (14), for lining a combustion-chamber wall (13), the chamber wall has a first wall (17) with a hot side (18) which can be loaded with a hot medium, a cold side (19) which lies opposite the hot side (18), and a circumferential edge (24) which extends on a first (20), a second (21) and a third narrow side (22) of the first wall (17) to a first height (25) beyond the cold side (19), the circumferential edge (24) extends on a fourth narrow side (23) to a second shorter height (26), substantially at the second height (26), a second wall (27) lies opposite the cold side (19) and extends over the width of the fourth narrow side (23) from the fourth narrow side (23) and over a part of the length of the narrow sides (20, 22), which adjoin the fourth narrow side; (23), the second wall (27) has an edge (29) at the end (28) thereof which faces away from the fourth narrow side (23), which edge (29) extends to the first height (25). Furthermore, a combustion chamber and a gas turbine are disclosed.Type: ApplicationFiled: March 12, 2013Publication date: January 29, 2015Applicant: Siemens AktiengesellschaftInventors: Francois Benkler, Thomas Brandenburg, Olga Deiss, Thomas Grieb, Marco Link, Nicolas Savilius, Daniel Vogtmann, Jan Wilkes
-
Publication number: 20150007573Abstract: An annular combustion chamber (1) for a gas turbine, the chamber having an outer shell (12) which has at least one inlet opening (4) for a burner (3) and an outlet (7) which opens into a turbine chamber (8), wherein ducts (14) which can be closed, which are oriented substantially parallel to the symmetry axis (2) of the annular combustion chamber (1), and through which final compressor air is guided into the annular combustion chamber (1) are provided in the outer shell (12) in the region of the outlet (7). Ring segments around the outer shell have projections selectively movable to at least partially block and open the ducts. A gas turbine is also disclosed.Type: ApplicationFiled: March 15, 2013Publication date: January 8, 2015Inventors: Francois Benkler, Thomas Brandenburg, Olga Deiss, Thomas Grieb, Marco Link, Nicolas Savilius, Daniel Vogtmann, Jan Wilkes
-
Patent number: 8800292Abstract: A heat shield element arrangement including a heat shield element for a heat shield arranged on a supporting structure is provided. On each of the two opposing sides running parallel to the installation grooves the heat shield element includes a continuous screw head opening which penetrates the cold side and the hot side of the heat shield element substantially vertically and through which the screw head of the respective screw is arranged to be accessible to the supporting structure, and a spring element may be arranged under the respective screw, which spring element may be extended along the hot side of the heat shield element and the parallel installation groove of the supporting structure. An outer end of the spring element is embodied as a clamping retaining hook which is provided for the purpose of engaging in the laterally recessed retaining groove of the heat shield element.Type: GrantFiled: June 8, 2010Date of Patent: August 12, 2014Assignee: Siemens AktiengesellschaftInventors: Andreas Böttcher, Andre Kluge, Marco Link, Wilhelm Scheidtmann, Gerhard Simon, Thomas-Dieter Tenrahm, Marc Tertilt, Sabine Tüschen
-
Publication number: 20140193241Abstract: An internally coolable component for a gas turbine with at least one cooling duct, on the inner surface of which swirl elements are arranged in the form of turbulators which extend transversely with respect to the main flow direction of a coolant is provided. In order to reduce pressure losses for the coolant in the cooling duct, pins with different heights are set up between the turbulators.Type: ApplicationFiled: August 2, 2012Publication date: July 10, 2014Applicant: SIEMENS AKTIENGESELLSCHAFTInventors: Marcel Eifel, Daniel Gloss, Andreas Heselhaus, Stephan Klumpp, Marco Link, Uwe Sieber, Stefan Volker, Michael Wagner
-
Passage wall section for an annular flow passage of an axial turbomachine with radial gap adjustment
Patent number: 8721270Abstract: A passage wall section of an annular flow passage of an axial turbomachine is provided. A guide ring has a first toothing arrangement which is in contact with a second toothing arrangement arranged on a sidewall of a circumferential groove which accommodates the guide ring, wherein for axial displacement of the displaceable guide ring, the guide ring is rotatable in a circumferential direction.Type: GrantFiled: May 10, 2011Date of Patent: May 13, 2014Assignee: Siemens AktiengesellschaftInventors: Richard Graefe, Carsten Kaufmann, Rafael Labisch, Marco Link, Oliver Schneider -
Publication number: 20130101422Abstract: A fastening assembly for blades of turbomachines through which axial flow can take place, preferably compressors, includes a blade carrier having a lateral face, in which retaining groves are distributed along the circumference, with blades being inserted in the grooves, wherein a resilient tensioning element is provided between each groove base and the underside of the respective blade foot, the underside being located opposite of the groove base. The tensioning element is supported on the respective underside and on the respective groove base in a pretensioning manner, wherein a channel is provided both in the groove base and in the underside, with the tensioning element resting in the channels.Type: ApplicationFiled: May 11, 2011Publication date: April 25, 2013Inventors: Patrick Bullinger, Marco Link, Nicolas Savilius, Uwe Sieber, Hubertus Michael Wigger
-
Publication number: 20120230829Abstract: A blade for a turbine or a compressor, at least partially made of fiber-reinforced plastic, in particular carbon fiber reinforced plastic, being particularly durable under operating conditions is provided. The blade includes a blade body and a blade root. The blade body is substantially made of a folded fabric web made of fiber reinforced plastic, wherein a retaining loop is formed in the area of the fold, and wherein a blade surface is formed in the area of the fold, and wherein a blade surface is formed from the overlapping web ends. The blade root includes a longitudinal beam and at least two holders for anchoring the blade in a corresponding groove of a rotor, the holders being preferably each fixedly connected to the beam at both ends. The blade body is suspended on the beam by means of the retaining loop.Type: ApplicationFiled: November 16, 2010Publication date: September 13, 2012Inventors: Francois Benkler, Marco Link, Torsten Matthias, Marc Mittelbach, Marion Morthorst, Michael Rollmann, Horst Saathoff, Hubertus Michael Wigger
-
Passage wall section for an annular flow passage of an axial turbomachine with radial gap adjustment
Publication number: 20110280712Abstract: A passage wall section of an annular flow passage of an axial turbomachine is provided. A guide ring has a first toothing arrangement which is in contact with a second toothing arrangement arranged on a sidewall of a circumferential groove which accommodates the guide ring, wherein for axial displacement of the displaceable guide ring, the guide ring is rotatable in a circumferential direction.Type: ApplicationFiled: May 10, 2011Publication date: November 17, 2011Inventors: Richard GRAEFE, Carsten KAUFMANN, Rafael LABISCH, Marco LINK, Oliver SCHNEIDER -
Publication number: 20100307162Abstract: A heat shield element arrangement including a heat shield element for a heat shield arranged on a supporting structure is provided. On each of the two opposing sides running parallel to the installation grooves the heat shield element includes a continuous screw head opening which penetrates the cold side and the hot side of the heat shield element substantially vertically and through which the screw head of the respective screw is arranged to be accessible to the supporting structure, and a spring element may be arranged under the respective screw, which spring element may be extended along the hot side of the heat shield element and the parallel installation groove of the supporting structure. An outer end of the spring element is embodied as a clamping retaining hook which is provided for the purpose of engaging in the laterally recessed retaining groove of the heat shield element.Type: ApplicationFiled: June 8, 2010Publication date: December 9, 2010Inventors: Andreas Bõttcher, Andre Kluge, Marco Link, Wilhelm Scheidtmann, Gerhard Simon, Thomas-Dieter Tenrahm, Marc Tertilt, Sabine Tüschen